Airplane engine mount



Feb. 16, 1937. Fz R CANNEY 2,070,782

AIRPLANE ENGINE MOUNT Filed Jan. sa, 1935 Fank R. Canne wwf-@f reamerel. 16,1937

aofiogsz nr erica makina; cmemco sm w Boe g meldt mm, e nu corporationotWashington ApplicationJ January'i, 1935, No. i373 2 claims. (01..,248-5)My invention relates to the means by which engines may be mounted upontheir vehicles, and more particularly to a mount Intended for radialairplane engines.

A powerful radial engine, mounted upon a relatively light aircraftstryuoture, subjects the latter to vibrational movements transversely,axially, and rotationally. Y 'Ihe latter is particularly strong,.because of the radial character of the engine, and under certainconditions or engine speeds, and when the engine is mounted on the endof a nacelle, spaced fromthe main spars or. other main structure of theairplane, as is frequently the case, this rotational movement becomesparticularly noticeable and objectionable. Practically speaking, it isnot possible to prevent some of these vibrations from being carried intothe airplane structur but if the engine is so mounted that it is free tovibrate rotationally through a damping medium between the engine Vandthe structure supporting it, most of the rotational vibration isabsorbed in the damping medium, and very little of it is transmitted tovthev aircraft structure.

' It is a further object of my invention to provide an improved type ofmounting and an improved mounting device having the advantages indicatedabove.

My invention comprises the novel mounting nfieans, and the novelcombination of engine, mounting ring, and mounting means, as shown inthe accompanying drawing, described in this specification, and as willbe more particularly deiincd by the claims -which terminate the same.'

En the accompanying drawing I have shown a typical form of engine andaircraft structure with my improved mounting means joining the two Ytogether,

Figure l is a side elevation of such an engine and engine mount, partsbeing broken away and shown in section.

Figure 2 is in general a section on the line 2 2 oi Figure 3, and Figure3 is a section on the line 3 3 ci Figure 2, illustrating the mountingthat illustrated is merely a typical and usually provided with holeswhich may be' brought into alignment with the holes oi' the lugs I8.

In the present form, however, the mounting ring 2 is made larger incircumference than the circle dened by the apertures I1 of the ears Il.

g and in positions to register with each oi' the ears I6 is providedwith a pair of spaced ears 3 which project inwardly or toward the centerof the' mounting ring and which as shown are inclined 10 somewhatrearwardly. Preferably each ear extends in a substantially radial plane.These ears 3 are suitably secured to the mounting ring, as for exampleby welding. They may be suitably braced or strengthenedcircumferentially oi' the mounting ring, if desired or found necessary.

The mounting means proper consists oi' a bolt f3 oia size to be receivedin the aperture I1, having formed upon one end ahead in the form of asleeve d@ which, as is indicated in 2o the drawing, is of metal,extending transversely to the bolt and generally equally spaced ateachside of the axis oi the bolt. The length of this sleeve, however, isless than the spacing between the two ears 3 of a pair. Within this 25sleeve may be mounted a second sleeve 4I, whichV is also shown in thedrawing to be made of metal, projecting at each end beyond the ends ofthe sleeve dll, and between these two sleeves is bonded a resilientmember such as the rubber 3o sleeve d?. A bolt 5 is passed throughapertures provided in the ears 3 and through the internal sleeve Iii,being secured by suitable means such as the nut 5u. Thus the'bolt 5 andthe three sleeves extend generally circumferentially of 35 themountingring 2, and the bolt 4 extends generally parallel to the axis of thismounting ring, and radially of the sleeve #30. The bolt d is held in itsengine lug by a nut 36, a washer d5 being interposed between it's head.and the 40 lug. With the engine thus held in a plurality of thesemounting devices, spaced circumferentially around the crank case, theengine may vibrate somewhat axially and somewhat transversely, but therubber sleeve will allow movement of the bolt E only to a limited extentin these. dl. rections, since they produce stresses transversely of theaxis of the sleeves, but the sleeves will permit more extended movementin the direction of their length, and as each of these sleeves extendscircumferentially, being spaced angularly from each other about themounting ring, the combined eect of this mounting is to permit aconsiderable amount of movement of the ring, s sleeve of a length lessthan the spac- A ing of said ears and received therebetween, and havinga bolt integral therewith and projecting radially outward therefrom forengagement with the engine, a second sleeve received concentrloallywithin said ilrst sleeve, and of s lengthto nt snugly between said ears,a bolt extending through said second sleeve and said ears, and a rubbersleeve interposed between said ilrst two sleeves and positively bondedto both thereof.

2. A device for resiliently mounting ga radial airplane engine upon amounting ring, comprising twoy concentric metal sleeves disposedcircumferentially of the mounting ring, a rubber sleeve interposedbetween said metal sleeves and positively bonded to both thereof, amember projecting radialiy'of the outer one of said metal sleeves andintegral therewith, for securement to the engine, means extending.radially oi the mounting ring, and engaging opposite ends oi.'

-said second sleeve, and means connecting said' first means with saidsecond sleeve.

FRANK R. CANNEY.

